EP2252784A2 - Bleed airflow balancing control using simplified sensing - Google Patents

Bleed airflow balancing control using simplified sensing

Info

Publication number
EP2252784A2
EP2252784A2 EP08871798A EP08871798A EP2252784A2 EP 2252784 A2 EP2252784 A2 EP 2252784A2 EP 08871798 A EP08871798 A EP 08871798A EP 08871798 A EP08871798 A EP 08871798A EP 2252784 A2 EP2252784 A2 EP 2252784A2
Authority
EP
European Patent Office
Prior art keywords
bleed air
air flow
differential pressure
pressure
bleed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08871798A
Other languages
German (de)
French (fr)
Other versions
EP2252784A4 (en
EP2252784B1 (en
Inventor
Oswaldo Barthel Monteiro
Vinicius Jorge Tin
Bernardo Campos Da Silva Franco
Ricardo José BARBOSA
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Embraer SA
Original Assignee
Embraer SA
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Filing date
Publication date
Application filed by Embraer SA filed Critical Embraer SA
Publication of EP2252784A2 publication Critical patent/EP2252784A2/en
Publication of EP2252784A4 publication Critical patent/EP2252784A4/en
Application granted granted Critical
Publication of EP2252784B1 publication Critical patent/EP2252784B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3015—Pressure differential pressure
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the technology herein relates to aircraft engine airflow control, and more particularly to bleed airflow balancing control using simplified pressure sensing. Still more particularly, an exemplary illustrative non-limiting implementation provides bleed airflow balancing using a single bi-directional differential pressure transducer and a single pressure transducer.
  • gas turbine engines 10 of the type commonly found on many aircraft include a compressor 20, a combuster 30 and a turbine 40.
  • the compressor 20 compresses air which is then mixed with fuel for combustor 30 to ignite.
  • the combustor 30 exhausts gases turn the vanes of the turbine(s) 40. Power from the rotating turbine 40 operates the compressor 20.
  • Turbine engine compressors 20 can be designed to supply more compressed air than is needed to operate the engine 10. This additional compressed air from the compressor 20 can be used for tasks other than feeding the combustor 30. For example, it is common to bleed some of the compressed air from the compressor 30 and route it to other equipment onboard the aircraft such as de-icers, cabin pressurization systems and the like. [0006] Each of the aircraft engines 10 can be used as a source for compressed bleed air. It is generally desirable to balance the amount of bleed air obtained from each pair of engines 10 to equalize wear and other engine operating conditions. Various techniques have been designed in the past to control such bleed air balancing.
  • FIG. 2 An exemplary prior art airflow balancing control 100 for a dual engine, dual bleed aircraft is shown in Figure 2.
  • hot bleed air flow from the compressor 30 of a first engine 10a is regulated by a first pressure regulating shutoff valve 110a
  • hot bleed air flow from the compressor 20 of a second engine 10b is regulated by a second pressure regulating shutoff valve 110b.
  • These two streams of regulated hot bleed air are provided to precoolers 112a, 112b that receive cold air from the fan or prop (in the case of a turboprop) on the front of the engines 10a, 10b.
  • the amount of cold air is also regulated by valves 114a, 114b.
  • precoolers 1 12a, 112b are provided to opposite input ports 116a, 116b of a T- configuration bleed air manifold 1 18.
  • the bleed air flow Upon entering the input ports 116a, 1 16b, the bleed air flow encounters temperature sensors 108a, 108b respectively that measure the bleed air temperature.
  • the two different bleed air streams are then passed through respective Venturis 120a, 120b before being combined into a common air supply to aircraft systems available at a manifold output port 122.
  • Differential pressure transducers 104a, 104b placed across each venturi 120a, 120b measures the bleed air flow pressure differential across the venturi's throat.
  • Pressure transducers 106a, 106b placed within the manifold 116 before the bleed air flow encounters the Venturis 120 measures the absolute pressure of each engine's bleed air flow.
  • digital controller 102 receives the signals provided by the two differential pressure transducers 104a, 104b, the two pressure transducers 106a, 106b and the two temperature sensors 108a, 108b. Digital controller 102 processes these signals to determine the mass air flow of each bleed air stream.
  • Control law software operating on the controller 102 calculates currents that are delivered to modulate the PRSOV 1 (Pressure Regulating Shutoff Valve) 110a and PRSOV 2 (Pressure Regulating Shutoff Valve) 110b butterflies that independently control how much air to bleed from the compressors 20 of each of engines 10a, 10b, respectively.
  • the controller 102 can dynamically balance the mass air flow from the respective bleed air streams to ensure that each engine 10a, 10b contributes exactly half of the total bleed air pressure provided at manifold output port 112.
  • the exemplary illustrative non-limiting controller 102 may implement a control law algorithmic process that processes these currents as follows.
  • the pressure delivered to the aircraft systems should stabilize in the desired set point in acceptable settling time; the respective pressure overshoot and undershoot should also be acceptable and under steady state condition; each engine should contribute half of the total air bleed flow.
  • An exemplary illustrative non-limiting method of controlling bleed air flow may comprise measuring the differential pressure between a first bleed air flow and a second bleed air flow; generating a differential pressure correction signal in response to said measured differential pressure; measuring the pressure of a bleed air flow obtained by combining said first and second bleed air flows; and controlling valves modulating said first and second bleed air flows based at least in part on said measured pressure and said differential pressure correction signal.
  • the method may further include measuring the temperature of said first bleed air flow and measuring the temperature of said second bleed air flow, and said controlling includes modulating said first and second bleed air flows in response to said measured temperatures.
  • the differential pressure measuring may comprise measuring the differential pressure between the throat of a first venturi through which said first bleed air flow passes, and the throat of a second venturi through which said second bleed air flow passed.
  • the differential pressure measuring may comprise measuring the differential pressure between two different regions of a manifold used to combine said first and second bleed air flows.
  • the method may further include deriving said first bleed air flow from a first gas turbine engine, and deriving said second bleed air flow from a second gas turbine engine.
  • the generating may includes applying a proportional gain, an integration and a differentiation.
  • the controlling may comprise controlling first and second pressure regulating shutoff valves.
  • a dual engine bleed airflow regulator may comprise a single pressure transducer that measures the pressure of combined first bleed air flow from a first engine and a second bleed air flow from a second engine; a single bi-directional differential pressure transducer that measures the difference between the pressure of said first bleed air flow and said second bleed air flow; and a controller responsive to said single differential pressure transducer and said single pressure transducer, said controller generating a first control signal for modulating said first bleed air flow and generating a second control signal for modulating said second bleed air flow.
  • Figure 1 shows an exemplary illustrative non-limiting aircraft gas turbine engine
  • Figure 2 is a block diagram of an exemplary illustrative non-limiting prior art dual bleed airflow balancing control
  • Figure 3 is an exemplary illustrative non-limiting improved bleed mass flow balancing control employing a reduced number of sensors;
  • Figure 4 shows an exemplary illustrative non-limiting pressure regulating shutoff valve control law control law architecture that may be implemented inside a digital controller;
  • Figure 5 shows exemplary illustrative non-limiting pressure shutoff valve control law architecture for a "venturiless" configuration.
  • a digital controller 202 processes the information provided by a single differential bi-directional pressure transducer 204, a single pressure transducer 206 and two temperature sensors 108a, 108b.
  • temperature sensor 108a senses the temperature of the bleed air stream from engine 10a
  • temperature sensor 108b senses the temperature of the bleed air stream from engine 10b as discussed in connection with Figure 2.
  • the differential pressure transducer 204 is no longer connected or disposed to monitor the pressure drop across either one of Venturis 120a, 120b.
  • the bi-directional differential pressure transducer 204 measures the difference between (a) the pressure after engine 10a's bleed air stream passes through the throat of venturi 120a, and (b) the pressure after engine 10b's bleed air stream passes through the throat of venture 120b.
  • pressure transducers 106a, 106b shown in Figure 2 can be eliminated, and a single pressure transducer 206 is now placed in the manifold output port 122 to sense the pressure of the combined bleed air flow from the pair of engines 10a and 10b.
  • Venturis 120a In the exemplary illustrative non-limiting implementation,
  • FIG. 4 An exemplary illustrative non-limiting pressure shutoff valve control law architecture or algorithm 300 that is implemented by digital controller 202 is shown in the Figure 4.
  • This exemplary illustrative non-limiting control law architecture 300 (implemented by software running on controller 202 in the illustrative non-limiting exemplary implementation) can be divided into two control loops 302, 304.
  • One control loop 302 is the pressure transducer loop.
  • Pressure control loop 302 calculates the average current to modulate the both PRSOV valve butterflies 110a, 1 10b in order to reach the desired pressure set point in an acceptable settling time, considering also acceptable pressure overshoots and undershoots.
  • the pressure sense output signal of pressure transducer 206 is combined with a pressure set point and is then applied to three different subchannels.
  • the first subchannel 302a provides a proportional gain.
  • the second subchannel 302b provides a dead zone (hysteresis) based integration gain and discrete time integration.
  • the third subchannel 302c provides a discrete gain that is differentiated using a discrete transfer function.
  • the second control loop 304 is the differential pressure transducer loop.
  • This differential pressure control loop 304 is used to annul or correct for the differential pressure between the left and right sides. Its set point is assumed to be 0 PSID in the exemplary illustrative non-limiting implementation, so no set point value combine is needed. After an acceptable transient period, the pressure in each venturi throat 120a, 120b converges to the same value. At this moment, it can be considered that bleed airflow from both engines 10a, 10b are symmetrically balanced.
  • the exemplary illustrative non-limiting implementation provides this processing using a proportional gain and an integrator gain that is integrated using a discrete time integration.
  • the outputs of control loops 302, 304 are combined and then applied to control each of valves 110a, 1 10b.
  • Clippers 305a, 305b may be used to prevent valves 110a, 110b from being overdriven.
  • an acceptable transducer drift may be identified and effectively compensated by the digital controller 202 during the system power-up (when there is zero pressure) and also considering that the differential pressure transducer loop 304 tries continuously to annul the differential pressure between the both Venturis, 120a, 120b, by providing a correction signal to the pressure control loop 302 output, this differential pressure control loop 304 is immune to transducer gain degradation.
  • differential pressure transducer 104b remains robust even as the system ages and the characteristics of differential pressure transducer 104b changes.
  • the change in characteristics of differential pressure transducer 104b affects the bleed air flow of both engines 104a, 104b equally.
  • the differential pressure transducer provides a "zero" adjustment in every A/C power up to compensate for any bias in the transducer, thus providing independence from drift.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
  • Control Of Fluid Pressure (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Measuring Fluid Pressure (AREA)

Abstract

A simplified air bleed balancing control system for a pair of aircraft gas turbine engines reduces the number of pressure transducers and differential pressure transducers. Advantages include lower weight, less expensive system, better total system MTBF (mean time before failure), acceptable differential pressure transducer drift identification and compensation by the digital controller, and fewer maintenance tasks.

Description

TITLE
BLEED AIRFLOW BALANCING CONTROL USING SIMPLIFIED SENSING
CROSS-REFERENCES TO RELATED APPLICATIONS
[0001] Not applicable.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
[0002] Not applicable.
TECHNICAL FIELD
[0003] The technology herein relates to aircraft engine airflow control, and more particularly to bleed airflow balancing control using simplified pressure sensing. Still more particularly, an exemplary illustrative non-limiting implementation provides bleed airflow balancing using a single bi-directional differential pressure transducer and a single pressure transducer.
BACKGROUND AND SUMMARY
[0004] As shown in Figure 1 , gas turbine engines 10 of the type commonly found on many aircraft include a compressor 20, a combuster 30 and a turbine 40. The compressor 20 compresses air which is then mixed with fuel for combustor 30 to ignite. The combustor 30 exhausts gases turn the vanes of the turbine(s) 40. Power from the rotating turbine 40 operates the compressor 20.
[0005] Turbine engine compressors 20 can be designed to supply more compressed air than is needed to operate the engine 10. This additional compressed air from the compressor 20 can be used for tasks other than feeding the combustor 30. For example, it is common to bleed some of the compressed air from the compressor 30 and route it to other equipment onboard the aircraft such as de-icers, cabin pressurization systems and the like. [0006] Each of the aircraft engines 10 can be used as a source for compressed bleed air. It is generally desirable to balance the amount of bleed air obtained from each pair of engines 10 to equalize wear and other engine operating conditions. Various techniques have been designed in the past to control such bleed air balancing. [0007] An exemplary prior art airflow balancing control 100 for a dual engine, dual bleed aircraft is shown in Figure 2. In this prior art exemplary design, hot bleed air flow from the compressor 30 of a first engine 10a is regulated by a first pressure regulating shutoff valve 110a, and hot bleed air flow from the compressor 20 of a second engine 10b is regulated by a second pressure regulating shutoff valve 110b. These two streams of regulated hot bleed air are provided to precoolers 112a, 112b that receive cold air from the fan or prop (in the case of a turboprop) on the front of the engines 10a, 10b. The amount of cold air is also regulated by valves 114a, 114b. The outputs of precoolers 1 12a, 112b are provided to opposite input ports 116a, 116b of a T- configuration bleed air manifold 1 18. Upon entering the input ports 116a, 1 16b, the bleed air flow encounters temperature sensors 108a, 108b respectively that measure the bleed air temperature. The two different bleed air streams are then passed through respective Venturis 120a, 120b before being combined into a common air supply to aircraft systems available at a manifold output port 122. Differential pressure transducers 104a, 104b placed across each venturi 120a, 120b measures the bleed air flow pressure differential across the venturi's throat. Pressure transducers 106a, 106b placed within the manifold 116 before the bleed air flow encounters the Venturis 120 measures the absolute pressure of each engine's bleed air flow. [0008] It can be observed that digital controller 102 receives the signals provided by the two differential pressure transducers 104a, 104b, the two pressure transducers 106a, 106b and the two temperature sensors 108a, 108b. Digital controller 102 processes these signals to determine the mass air flow of each bleed air stream. Control law software operating on the controller 102 calculates currents that are delivered to modulate the PRSOV 1 (Pressure Regulating Shutoff Valve) 110a and PRSOV 2 (Pressure Regulating Shutoff Valve) 110b butterflies that independently control how much air to bleed from the compressors 20 of each of engines 10a, 10b, respectively. In this way, the controller 102 can dynamically balance the mass air flow from the respective bleed air streams to ensure that each engine 10a, 10b contributes exactly half of the total bleed air pressure provided at manifold output port 112. [0009] Generally speaking, the exemplary illustrative non-limiting controller 102 may implement a control law algorithmic process that processes these currents as follows. The pressure delivered to the aircraft systems should stabilize in the desired set point in acceptable settling time; the respective pressure overshoot and undershoot should also be acceptable and under steady state condition; each engine should contribute half of the total air bleed flow.
[0010] While much work has been done in the past, further improvements are possible and desirable. In particular, it would be highly advantageous to simplify the air bleed balancing control system described above to reduce the number of pressure transducers, to reduce system weight and to optimize the bleed balancing control system.
[0011] An exemplary illustrative non-limiting method of controlling bleed air flow may comprise measuring the differential pressure between a first bleed air flow and a second bleed air flow; generating a differential pressure correction signal in response to said measured differential pressure; measuring the pressure of a bleed air flow obtained by combining said first and second bleed air flows; and controlling valves modulating said first and second bleed air flows based at least in part on said measured pressure and said differential pressure correction signal.
[0012] The method may further include measuring the temperature of said first bleed air flow and measuring the temperature of said second bleed air flow, and said controlling includes modulating said first and second bleed air flows in response to said measured temperatures. The differential pressure measuring may comprise measuring the differential pressure between the throat of a first venturi through which said first bleed air flow passes, and the throat of a second venturi through which said second bleed air flow passed. The differential pressure measuring may comprise measuring the differential pressure between two different regions of a manifold used to combine said first and second bleed air flows. The method may further include deriving said first bleed air flow from a first gas turbine engine, and deriving said second bleed air flow from a second gas turbine engine. The generating may includes applying a proportional gain, an integration and a differentiation. The controlling may comprise controlling first and second pressure regulating shutoff valves.
[0013] A dual engine bleed airflow regulator may comprise a single pressure transducer that measures the pressure of combined first bleed air flow from a first engine and a second bleed air flow from a second engine; a single bi-directional differential pressure transducer that measures the difference between the pressure of said first bleed air flow and said second bleed air flow; and a controller responsive to said single differential pressure transducer and said single pressure transducer, said controller generating a first control signal for modulating said first bleed air flow and generating a second control signal for modulating said second bleed air flow. [0014] Non-limiting exemplary illustrative features and advantages include:
• Reduced number of pressure transducers.
• Reduced number of differential pressure transducers.
• Lower weight.
• Less expensive system.
• Acceptable differential pressure transducer drift identification and compensation by the digital controller during the system power-up (when there is zero pressure)
• Better total system MTBF (mean time before failure) and, consequently, it requires less maintenance tasks.
BRIEF DESCRIPTION OF THE DRAWINGS
[0015] These and other features and advantages will be better and more completely understood by referring to the following detailed description of exemplary non-limiting illustrative embodiments in conjunction with the drawings of which:
[0016] Figure 1 shows an exemplary illustrative non-limiting aircraft gas turbine engine;
[0017] Figure 2 is a block diagram of an exemplary illustrative non-limiting prior art dual bleed airflow balancing control;
[0018] Figure 3 is an exemplary illustrative non-limiting improved bleed mass flow balancing control employing a reduced number of sensors; [0019] Figure 4 shows an exemplary illustrative non-limiting pressure regulating shutoff valve control law control law architecture that may be implemented inside a digital controller; and
[0020] Figure 5 shows exemplary illustrative non-limiting pressure shutoff valve control law architecture for a "venturiless" configuration.
DETAILED DESCRIPTION
[0021] In the Fig. 3 exemplary illustrative non-limiting implementation for a pair of engines 10a, 10b, a digital controller 202 processes the information provided by a single differential bi-directional pressure transducer 204, a single pressure transducer 206 and two temperature sensors 108a, 108b. In this exemplary illustrative non-limiting implementation, temperature sensor 108a senses the temperature of the bleed air stream from engine 10a, and temperature sensor 108b senses the temperature of the bleed air stream from engine 10b as discussed in connection with Figure 2. However, in this exemplary illustrative non-limiting implementation, the differential pressure transducer 204 is no longer connected or disposed to monitor the pressure drop across either one of Venturis 120a, 120b. Instead, the bi-directional differential pressure transducer 204 measures the difference between (a) the pressure after engine 10a's bleed air stream passes through the throat of venturi 120a, and (b) the pressure after engine 10b's bleed air stream passes through the throat of venture 120b. Furthermore, pressure transducers 106a, 106b shown in Figure 2 can be eliminated, and a single pressure transducer 206 is now placed in the manifold output port 122 to sense the pressure of the combined bleed air flow from the pair of engines 10a and 10b. [0022] In the exemplary illustrative non-limiting implementation, Venturis 120a,
120b are preferably configured identically, so it is assumed that the pressure difference caused by passage through each venture 120a, 120b is almost or substantially the same. In other words, after the both Venturis 120a, 120b, it is assumed that the "T" duct output port 122 has symmetrical dimensions with respect to each of engine 10a, 10b bleed air flows. It is also assumed that both Fan Air Valve 114a, 114b control loops are adjusted to the same temperature set point. Therefore, after a transient period is over and the system reaches steady state, both side temperatures can be considered almost the same.
[0023] An exemplary illustrative non-limiting pressure shutoff valve control law architecture or algorithm 300 that is implemented by digital controller 202 is shown in the Figure 4. This exemplary illustrative non-limiting control law architecture 300 (implemented by software running on controller 202 in the illustrative non-limiting exemplary implementation) can be divided into two control loops 302, 304. [0024] One control loop 302 is the pressure transducer loop. Pressure control loop 302 calculates the average current to modulate the both PRSOV valve butterflies 110a, 1 10b in order to reach the desired pressure set point in an acceptable settling time, considering also acceptable pressure overshoots and undershoots. In more detail, the pressure sense output signal of pressure transducer 206 is combined with a pressure set point and is then applied to three different subchannels. The first subchannel 302a provides a proportional gain. The second subchannel 302b provides a dead zone (hysteresis) based integration gain and discrete time integration. The third subchannel 302c provides a discrete gain that is differentiated using a discrete transfer function. These three processed subchannel outputs are available for combining according to a predetermined function.
[0025] The second control loop 304 is the differential pressure transducer loop.
This differential pressure control loop 304 is used to annul or correct for the differential pressure between the left and right sides. Its set point is assumed to be 0 PSID in the exemplary illustrative non-limiting implementation, so no set point value combine is needed. After an acceptable transient period, the pressure in each venturi throat 120a, 120b converges to the same value. At this moment, it can be considered that bleed airflow from both engines 10a, 10b are symmetrically balanced. The exemplary illustrative non-limiting implementation provides this processing using a proportional gain and an integrator gain that is integrated using a discrete time integration. [0026] In the exemplary illustrative non-limiting implementation, the outputs of control loops 302, 304 are combined and then applied to control each of valves 110a, 1 10b. Clippers 305a, 305b may be used to prevent valves 110a, 110b from being overdriven. [0027] Considering that an acceptable transducer drift may be identified and effectively compensated by the digital controller 202 during the system power-up (when there is zero pressure) and also considering that the differential pressure transducer loop 304 tries continuously to annul the differential pressure between the both Venturis, 120a, 120b, by providing a correction signal to the pressure control loop 302 output, this differential pressure control loop 304 is immune to transducer gain degradation. In other words, the proposed configuration remains robust even as the system ages and the characteristics of differential pressure transducer 104b changes. The change in characteristics of differential pressure transducer 104b affects the bleed air flow of both engines 104a, 104b equally. The differential pressure transducer provides a "zero" adjustment in every A/C power up to compensate for any bias in the transducer, thus providing independence from drift.
[0028] The risk of unstable interactions between the different PRSOVs 110a,
110b (which are designed to have identical characteristics but may not in fact have identical characteristics) is reduced because the pressure transducer loop 302 provides simultaneously the same average current for both valves. [0029] In a further exemplary illustrative non-limiting implementation, if it is possible to obtain a significant pressure drop in the "T" duct of manifold 1 16, then both Venturis 120a, 120b can be removed. In this case, the bi-directional differential pressure transducer 204 shall measure the differential pressure drop between the both sides of the "T" duct. Since the pressure drop increases when the flow increases (the pressure in the venturi throat has an inverted behavior), then the differential pressure signal provided by the differential transducer shall be inverted. An exemplary illustrative non- limiting modified control law architecture 300' shown in the Figure 4 includes an additional inverter 304a.
[0030] While the technology herein has been described in connection with exemplary illustrative non-limiting embodiments, the invention is not to be limited by the disclosure. For example, the system can modified to provide bleed air flow balancing for a system providing more than two engines. The invention is intended to be defined by the claims and to cover all corresponding and equivalent arrangements whether or not specifically disclosed herein.

Claims

WE CLAIM
1. A method of controlling bleed air flow comprising:
(a) measuring the differential pressure between a first bleed air flow and a second bleed air flow;
(b) generating a differential pressure correction signal in response to said measured differential pressure;
(c) measuring the pressure of a bleed air flow obtained by combining said first and second bleed air flows; and
(d) controlling valves modulating said first and second bleed air flows based at least in part on said measured pressure and said differential pressure correction signal.
2. The method of claim 1 further including measuring the temperature of said first bleed air flow and measuring the temperature of said second bleed air flow, and said controlling includes modulating said first and second bleed air flows in response to said measured temperatures.
3. The method of claim 1 wherein said differential pressure measuring comprises measuring the differential pressure between the throat of a first venturi through which said first bleed air flow passes, and the throat of a second venturi through which said second bleed air flow passes.
4. The method of claim 1 wherein said differential pressure measuring comprises measuring the differential pressure between two different regions of a manifold used to combine said first and second bleed air flows.
5. The method of claim 1 further including deriving said first bleed air flow from a first gas turbine engine, and deriving said second bleed air flow from a second gas turbine engine.
6. The method of claim 1 wherein said generating includes applying a proportional gain, an integration and a differentiation.
7. The method of claim 1 wherein said controlling comprises controlling first and second pressure regulating shutoff valves.
8. A dual engine bleed airflow regulator comprising: a single pressure transducer that measures the pressure of combined first bleed air flow from a first engine and a second bleed air flow from a second engine; a single differential pressure transducer that measures the difference between the pressure of said first bleed air flow and said second bleed air flow; and a controller responsive to said single differential pressure transducer and said single pressure transducer, said controller generating a first control signal for modulating said first bleed air flow and generating a second control signal for modulating said second bleed air flow.
EP08871798.8A 2008-01-31 2008-12-05 Bleed airflow balancing control using simplified sensing Not-in-force EP2252784B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/023,585 US8033118B2 (en) 2008-01-31 2008-01-31 Bleed airflow balancing control using simplified sensing
PCT/BR2008/000380 WO2009094734A2 (en) 2008-01-31 2008-12-05 Bleed airflow balancing control using simplified sensing

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EP2252784A2 true EP2252784A2 (en) 2010-11-24
EP2252784A4 EP2252784A4 (en) 2013-12-25
EP2252784B1 EP2252784B1 (en) 2016-05-25

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US8033118B2 (en) 2011-10-11
EP2252784A4 (en) 2013-12-25
WO2009094734A2 (en) 2009-08-06
EP2252784B1 (en) 2016-05-25
US20090193811A1 (en) 2009-08-06
WO2009094734A3 (en) 2010-02-04

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